US9244155B2 - Adaptive electronically steerable array (AESA) system for multi-band and multi-aperture operation and method for maintaining data links with one or more stations in different frequency bands - Google Patents

Adaptive electronically steerable array (AESA) system for multi-band and multi-aperture operation and method for maintaining data links with one or more stations in different frequency bands Download PDF

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US9244155B2
US9244155B2 US13/357,933 US201213357933A US9244155B2 US 9244155 B2 US9244155 B2 US 9244155B2 US 201213357933 A US201213357933 A US 201213357933A US 9244155 B2 US9244155 B2 US 9244155B2
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frequency band
communication station
communicating
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arrays
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US20120200449A1 (en
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Michael S. Bielas
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Raytheon Co
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/003—Transmission of data between radar, sonar or lidar systems and remote stations
    • G01S7/006—Transmission of data between radar, sonar or lidar systems and remote stations using shared front-end circuitry, e.g. antennas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/306—Details for transmitting guidance signals
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/281—Nose antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/0006—Particular feeding systems
    • H01Q21/0025—Modular arrays
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/0006—Particular feeding systems
    • H01Q21/0037—Particular feeding systems linear waveguide fed arrays
    • H01Q21/0043—Slotted waveguides
    • H01Q21/005—Slotted waveguides arrays
    • H01Q21/0056—Conically or cylindrically arrayed
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
    • H01Q3/2605—Array of radiating elements provided with a feedback control over the element weights, e.g. adaptive arrays
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S2013/0236—Special technical features
    • G01S2013/0245—Radar with phased array antenna
    • G01S2013/0254—Active array antenna
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S2013/0236—Special technical features
    • G01S2013/0272—Multifunction radar
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/30—Combinations of separate antenna units operating in different wavebands and connected to a common feeder system

Definitions

  • Embodiments pertain to adaptive electronically steerable arrays (AESAs). Some embodiments relate to AESA-based data links for interceptors, including next generation interceptor (NGIs).
  • AESA-based data links for interceptors, including next generation interceptor (NGIs).
  • NTIs next generation interceptor
  • FIG. 1 illustrates a system environment in accordance with some embodiments
  • FIGS. 2A and 2B illustrate an adaptive electronically steerable array (AESA) in accordance with some embodiments
  • FIG. 3 is a directivity pattern of an AESA in accordance with some embodiments.
  • FIG. 4 shows scan loss as a function of scan angle of an AESA in accordance with some embodiments
  • FIG. 5 illustrates a functional block diagram of a portion of an AESA system in accordance with some embodiments
  • FIG. 6 illustrates a functional block diagram of an AESA data link system architecture in accordance with some other embodiments.
  • FIGS. 7A , 7 B and 7 C illustrate some various AESA vehicle placements and configurations in accordance with some other embodiments.
  • FIG. 1 illustrates a system environment in accordance with some embodiments.
  • a vehicle 102 may include one or more suitable adaptive electronically steerable arrays (AESAs) 112 .
  • Each array 112 may include a plurality of radiating elements and control circuitry 110 to configure the elements for multi-band and multi-aperture operations.
  • AESAs adaptive electronically steerable arrays
  • CONOPS enhanced concept of operations
  • the control circuitry 110 may be configured to use a line-of-sight (LOS) vector to direct the array 112 for communications with a communication station 104 as the vehicle 102 maneuvers.
  • the vehicle 102 may be an interceptor such as a kill-vehicle or missile, although the scope of the embodiments is not limited in this respect.
  • the vehicle 102 may include aircraft including drones and unmanned aerial vehicles (UAVs).
  • the communication stations 104 may be ground based, ship-based, aircraft-based or satellite-based communication stations. In these embodiments, the control circuitry 110 may be configured to steer the array 112 to maintain communications with one or more communication stations 104 during the flight path of the vehicle 102 .
  • the ground and ship based communication stations may be ground or ship based radars configured for tracking targets as well as communicating with vehicles such as interceptors.
  • a satellite-based communication station 106 may act as a relay station for communications with a ground, ship or aircraft-based communication station. Accordingly, communication links with the communication stations 104 may be maintained as the vehicle 102 maneuvers.
  • control circuitry 110 may be configured to use the LOS vector to reconfigure the array 112 to switch between communicating with a first communication station 104 A and a second communication station 104 B.
  • an X-band link 103 may be established for communicating with a first communication station 104 A
  • an S-band link 105 may be established for communicating with a second communication station 104 B.
  • the second communication station 104 B may be over-the-horizon with respect to the first communication station 104 A and the control circuitry may be configured to cause the array 112 to switch between communicating with the first communication station 104 A and the second communication station 104 B at some point during the flight path of the interceptor 102 .
  • the use of a LOS vector allows the control circuitry 110 to direct communications (i.e., direct one or more antenna beams) toward one or more of the communication stations 104 . Accordingly, a communication link with at least one communication station 104 may be maintained during the flight path as the vehicle 102 maneuvers. The switching and handing-off of communications between communication stations 104 in this manner may provide for a significant range extension for interceptors. In some embodiments, the switching from S-band to X-band may occur after launch.
  • one communication station 104 may be an Army Navy/Transportable Radar Surveillance (AN/TPY-2) uplink system (radar and communication)
  • another communication station 104 e.g., communication station 104 B
  • AN/SPY-2 AN/SPY-2
  • Other types of communication stations are also suitable.
  • FIGS. 2A and 2B illustrate an adaptive electronically steerable array (AESA) in accordance with some embodiments.
  • the array 112 comprises a plurality of radiating elements 214 .
  • FIG. 2A illustrates a top and a side view of an AESA 112 and
  • FIG. 2B illustrates a perspective view of an AESA 112 .
  • each of the elements may comprise a patch antenna, while in other embodiments, dipole antennas, such as L-Band dipoles may be used, although the scope of the embodiments is not limited in this respect.
  • the array 112 may comprise a plurality of tile-modules where each element may be associated with a single tile. These embodiments allow the array to be curved to match the curvature of the interceptor.
  • radiating elements 214 may comprise may comprise directional or omnidirectional antennas, including, for example, dipole antennas, monopole antennas, patch antennas, loop antennas, microstrip antennas or other types of antennas suitable for transmission of RF signals.
  • higher power amplifier devices may be utilized for transmitting.
  • a reduced duty-cycle of between 5 to 10 percent, for example may be utilized when communicating with radar stations rather than a more conventional fifty-percent transmit/receive duty cycle. In this way, the excess heat generated by the higher power amplifier devices may be less of a concern.
  • Lower duty cycles are a characteristic of operating with radars as communications links since radar loading (for example tracking and surveillance) prohibits much time to be dedicated to communications; hence the lower duty cycle.
  • control circuitry 110 may be further configured to switch between communicating within a first frequency band through a first aperture to communicating within a second frequency band through a second aperture.
  • the first and second frequency bands may be widely-spaced frequency bands having at least a five percent carrier frequency separation, although this is not a requirement.
  • widely-spaced frequency bands may refer to frequency bands that are outside of the radio's instantaneous bandwidth (e.g., on the order of 10 MHz to 20 MHz) or outside of the antenna's resonate frequency (e.g., typically about 5% of the carrier frequency).
  • Widely-spaced frequency bands may also refer to different bands as defined by the FCC or ITU such as VHF, UHF, L, S, Ku, K, Ka, etc.
  • the first frequency band is a higher-frequency band than the second frequency band.
  • the control circuitry 110 may configure each element 214 as a single aperture for communicating within the first frequency band and may configure a plurality of two or more elements 214 to operate as a single aperture for communicating within the second frequency band.
  • the control circuitry 110 may be configured to coherently combine signals for the two or more elements for single-aperture operation.
  • the two or more elements 214 that operate as a single aperture are treated as a single element from the perspective of beam directing and steering (e.g., each element would have the same phase shift). This is unlike a conventional shared-aperture in which a single aperture is used for communicating with two or more communication stations.
  • control circuitry 110 configures a perfect-square number of elements 214 to operate as a single aperture for communicating within the second frequency band although the scope of the embodiments is not limited in this respect.
  • groups of four, nine or sixteen elements of the array 112 arranged in a square may be configured to operate as a single aperture for communicating within one or more secondary frequency bands.
  • the number of elements 214 used may be selectable to change the antenna pattern as well as the size and shape of the array for different transmit and receive capabilities.
  • the first frequency band is X-band and the second frequency band is S-band.
  • each element 214 may be configured to operate as a single aperture.
  • squares of four elements 214 may be configured to operate as a single aperture.
  • X-band operations may utilize sixty-four different apertures
  • S-band operations may utilize sixteen different apertures (e.g., 4 ⁇ 4 element squares).
  • S-band operates with fewer effective elements than X-band possibly resulting in a lower-antenna gain
  • S-band enjoys a path-loss advantage (because path loss scales as 20 log 10 of the frequency) over X-band diminishing many performance tradeoffs between the bands.
  • an 8 ⁇ 12 element X-band array may operate as a 2 ⁇ 3 aperture S-band array.
  • These embodiments may be configured to provide additional gain in certain directions.
  • a 128 ⁇ 8 element array may be used.
  • the array 112 may be configured for communications within additional frequency bands by configuring additional numbers of elements 214 as a single aperture.
  • higher frequency band e.g., X-band
  • mid-range frequency band e.g., S-band
  • four-element apertures e.g., 4 ⁇ 4 element squares
  • lower-frequency band communications may utilize nine-element apertures (e.g., 3 ⁇ 3 element squares).
  • FIG. 3 is a directivity pattern of an AESA in accordance with some embodiment.
  • the control circuitry 110 may be configured to provide nearly a sin(x)/(x) amplitude pattern across the elements 214 ( FIGS. 2A and 2B ).
  • the particular pattern may be determined by the configuration of the elements 214 (e.g., square or rectangular or other configuration) as well as the frequency, amplitude and phase of the signals.
  • the control circuitry 110 may be configured to communicate using different waveforms and switch between waveforms depending on the particular communication station 104 .
  • the example directivity pattern illustrated in FIG. 3 is for an 8 ⁇ 8 square array having a gain of 21 dB and 30 degrees of steering in the phi and theta axes.
  • the communication station 104 may be a radar tracking station configured to track a moving target and provide target tracking data to the interceptor over a link established with the interceptor using the array.
  • the interceptor may be configured to intercept the moving target using the target tracking data provided by a radar tracking station over the link.
  • the interceptor may switch between frequencies and apertures to switch between radar tracking stations. This may allow for over-the-horizon range extensions.
  • FIG. 4 shows scan loss as a function of scan angle of an AESA in accordance with some embodiments.
  • Scan loss is the effect is due to coupled E-field interactions between elements as the bean angle deviates from normal.
  • FIG. 4 shows this effect for selected scan loss functions.
  • scan loss is shown as a function of scan angle for three representative cases.
  • the scan loss may scale as cos f (alpha) where f is a factor such as 1.3, and alpha is scan angle. Since the beam is typically not steered beyond plus or minus 60 degrees excessive scan loss is avoided.
  • FIG. 5 illustrates a functional block diagram of a portion of an AESA system in accordance with some embodiments.
  • FIG. 5 illustrates how an AESA may be combined with a modem to produce a data link.
  • the AESA system 500 includes one or more arrays 112 , control circuitry 110 and modem and clock source circuitry 508 .
  • the control circuitry 110 may configure the modem and clock source circuitry 508 and the array 112 to provide a data link.
  • the modem and clock source circuitry 508 may provide array control signals and array power signals to the array 112 to perform the various operations described herein.
  • FIG. 6 illustrates a functional block diagram of an AESA in accordance with some other embodiments.
  • an AESA system 600 may include a plurality of arrays 112 .
  • the system includes switching circuitry 604 that is configured by the control circuitry 110 to switch between the arrays 112 of the plurality as the vehicle 102 ( FIG. 1 ) spins and maneuvers to maintain communications with one or more communication stations.
  • the switching circuitry 604 may comprise an RF switch.
  • the example architecture illustrated in FIG. 6 uses three arrays and a MODEM that can be mounted on a vehicle to obtain nearly omni-directional performance. More or fewer AESAs 112 may be used on a vehicle 102 .
  • each array 112 of the plurality may be positioned around the vehicle 102 at different angular-fields of regard. For example, when two arrays 112 are used, each array 112 may be provided at the 180 degree positions, when three arrays 112 are used, each array 112 may be provided at the 120 degree positions, and when four arrays 112 are used, each array 112 may be provided at the 90 degree positions. In some embodiments, each array 112 may be tilted forward or backward with respect to the front or the back of the vehicle 102 to achieve improved capability in either the forward or backward direction. In some embodiments, one array 112 may be provided between each divert thruster of an interceptor, although the scope of the embodiments is not limited in this respect.
  • FIGS. 7A , 7 B and 7 C illustrate some various AESA configurations in accordance with some other embodiments.
  • AESAs are located circumferentially around a vehicle.
  • the arrays may be located in front of and/or in back of each other.
  • FIG. 7A illustrates the positioning of AESAs 712 at the approximately 120 degree positions on vehicle 702 in which each AESA is configured for both receiving and transmitting in more than one frequency band.
  • Each AESA 712 may correspond to an array 112 ( FIG. 1 ).
  • FIG. 7B illustrates the positioning of AESAs 722 B configured for receiving at approximately 120 degree positions and the positioning of AESAs 722 A configured for transmitting at approximately 120 degree positions on vehicle 702 .
  • Each AESA 722 A and 722 B may correspond to an array 112 ( FIG. 1 ).
  • the AESAs 722 B may be separated from the AESAs 722 A by approximately sixty-degrees.
  • each AESA 722 A and 722 B may be is configured for communicating in more than one frequency band (e.g., X-band and S-band).
  • FIG. 7C illustrates the positioning of AESAs 732 B configured for communicating in a first frequency band (e.g., S-band) at approximately 120 degree positions and the positioning of AESAs 732 A configured for communicating in a second frequency band (e.g., X-band) at the other approximately 120 degree positions on the vehicle 702 .
  • Each AESA 732 A and 73 B may correspond to an array 112 ( FIG. 1 ).
  • the AESAs 732 B may be separated from the AESAs 732 A by approximately sixty-degrees.
  • each AESA 732 A and 732 B may be configured for transmitting and receiving in a single frequency band (e.g., either X-band or S-band).
  • an AESA 112 may be suitable for providing an AESA-Based Data Link for next generation interceptors (NGI).
  • NGI next generation interceptors
  • V bo high interceptor burnout velocities
  • KV kill vehicle
  • ⁇ V divert velocities
  • the high V bo and ⁇ V may be achieved by using low weight components.
  • the effectiveness (i.e., a high probability of kill) of a NGI may be increased with addition of a robust communications system on a maneuvering KV or missile.
  • Embodiments disclosed herein provide a communications approach that supports the current CONOPS and architectures of legacy communications systems, and may readily enable, scale and interoperate with advancements in CONOPS and other architectures.
  • the AESA system may provide an evolved data link with a multiband frequency capability such as X or S band and/or others and can interoperate with different waveforms.
  • a communication system approach is disclosed herein that uses lightweight communications devices (AESA-based data links) that may meet the objectives of NGI (for example maneuvering, rolling vehicles) within the corresponding architecture advancements that retain interoperability with legacy systems.
  • AESA-based data links lightweight communications devices
  • NGI for example maneuvering, rolling vehicles
  • AESA-based Data links for KV or missile on NGI may meet the challenge of high V bo and ⁇ V, and the challenge of expanding CONOPS and capabilities. This is evidenced by the fact that Active Electronically Steerable Array (AESA) antennas are suitable for radars and are having a similar beneficial impact on communications. AESAs also provide significant communications link performance over standard antennas such as, quasi-omni (switched) antennas, and other steerable approaches such as the Rotman lens or Butler-matrix antennas.
  • AESA Active Electronically Steerable Array
  • An AESA-based data link achieves improved performance with the significantly low, weight, small volume, low DC power, and high EIRP.
  • An AESA-based data link may be especially well suited to handle extreme vehicle dynamics while maintaining link margin such as with roll rates approaching several revolutions per second.
  • the AESA 112 may enjoy many advantages for use in military applications. These include lightweight, small volume, low DC power, solid-state reliability and manufacturability, modest production costs compared to discrete RF components, simple thermal management for small array sizes, allow for continuous communications, wideband high data rate operation, have a scalable physical level architecture, support HAENS environments in higher frequency bands (X-band and higher). In addition, steerable arrays provide nearly omni-directional performance despite a vehicle's attitude. High roll rates can be accommodated with simple algorithms.
  • a steerable narrow beam-width high-gain pattern from an AESA in accordance with embodiments has been simulated and its performance parameters calculated.
  • a square array such as the AESA of FIG. 2A
  • may exhibit 21 dB of gain may have the pattern shown in FIG. 3 .
  • Gain is defined as directivity plus losses.
  • S and X band are discussed but since dual or multi-band AESA apertures are feasible the invention is not limited in this respect.
  • the directivity pattern illustrated in FIG. 3 is for an 8 ⁇ 8 square array having a gain of 21 dB and 30 degrees of steering in the phi and theta axes. In these embodiments, since
  • the gain in dB is approximately be 10 log(N 2 )+3 dB.
  • S-band arrays will have fewer elements while being the same size as an X-band array since the free-space path loss goes as 20 log(f). Hence, S-band enjoys a 10 dB advantage in path loss over X-band that results in arrays that have approximately the same physical volume.
  • An S-band AESA may enjoy some advantages in element power density so that there is no significant penalty between S-band and X-band regarding the array size. For dual aperture arrays a trade may be accomplished that favors either the S or X band efficiencies depending on the need.
  • the antenna beamwidth may be nearly inversely proportional to the array dimensions and proportional to the wavelength.
  • the same array with 16 elements yields a beamwidth of 40.9 degrees.
  • Embodiments may be implemented in one or a combination of hardware, firmware and software. Embodiments may also be implemented as instructions stored on a computer-readable storage device, which may be read and executed by at least one processor to perform the operations described herein.
  • a computer-readable storage device may include any non-transitory mechanism for storing information in a form readable by a machine (e.g., a computer).
  • a computer-readable storage device may include read-only memory (ROM), random-access memory (RAM), magnetic disk storage media, optical storage media, flash-memory devices, and other storage devices and media.
  • the AESA system may include one or more processors and may be configured with instructions stored on a computer-readable storage device.

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WO2012109016A3 (fr) 2014-04-10
EP2673656A2 (fr) 2013-12-18

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